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SmallSats, Iodine Propulsion Technology, Applications to Low-Cost Lunar Missions, and the iodine Satellite (iSAT) Project. Presented to Lunar Exploration Analysis Group (LEAG) October 23, 2014 The SmallSat Market SmallSat Applications – USASMDC / ARSTRAT Low Cost • Per-Unit Cost Very Low • Enables Affordable Satellite Constellations • Minimal Personnel and Logistics Tail • Frequent Technology Refresh Survivability • Fly Above Threats and Crowded Airspace • Rapid Augmentation and Reconstitution • Very Small Target Responsiveness • Short-Notice Deployment • Tasked from Theater • Persistent and Globally Available • Can Adapt to the Threat DISTRIBUTION A. Approved for public release; 24 July 2013 Release Number 3105 Why Iodine? • Today’s SmallSats have limited propulsion capability and most spacecraft have none • The State of the Art is cold gas propulsion providing 10s of m/s ∆V • No solutions exist for significant altitude or plane change, or de-orbit from high altitude • SmallSat secondary payloads have significant constraints • No hazardous propellants allowed • Limited stored energy allowed • Limited volume available • Indefinite quiescent waiting for launch integration • Iodine is uniquely suited for SmallSat applications • Iodine electric propulsion provides the high ISP * Density (i.e. ∆V per unit volume) • 1U of iodine on a 12U vehicle can provide more than 5 km/s ∆V • Enables transfer to high value operations orbits • Enables constellation deployment from a single launch • Enables de-orbit from high altitude deployment (ODAR Compliance) • Iodine enables > 10km/s for ESPA Class Spacecraft • GTO deployment to GEO, Lunar Orbits, Near Earth Asteroids, Mars and Venus • Reduces launch access by 90% • Reduces mission life cycle cost by 30 – 80% • Iodine is a solid at ambient conditions, can launch unpressurized and sit quiescent indefinitely • The technology leverages high heritage xenon Hall systems • All systems currently at TRL 5 with maturation funded to achieve TRL 6 in FY16 • The iSAT System is planned for launch readiness in early 2017 Iodine vs. Alternatives Propellant Storage Density Boiling Point, oC Melting Point, oC Vapor Pressure @ 20oC Xe (SOA) 1.6 g/cm3 -108.1 oC -111.8 oC Supercritical (>15MPa) Iodine 4.9 g/cm3 184.3 oC 113.7 oC 40 Pa (0.0004 atm) Bismuth 9.8 g/cm3 1,564 oC 271.4 oC Solid Magnesium 1.74 g/cm3 1,091 oC 650 oC Solid Iodine has unique characteristics well suited for mission application Microsatellite Advantages Primary mission advantages are due to 1) Increased ISP * Density 2) Low storage pressure Microsatellites are extremely volume constrained Geocentric MicroSat Application Large increase in demand for MicroSat constellations and responsive space capabilities. - The 12U with 5kg of iodine can perform 4km/s ∆V - 20,000km altitude change - 30o inclination change from LEO - 80o inclination change from GEO - Larger spacecraft can perform even greater ∆V Iodine in enabling for rapidly growing spacecraft market. Interplanetary MicroSat NASA is pursing interplanetary MicroSat missions - INSPIRE selected as first interplanetary CubeSat – no propulsion - NASA HEOMD AES funding NEA Scout – solar sail propulsion - NASA HEOMD AES funding Lunar Flashlight – solar sail propulsion - High pressure and hazardous propellants are not allowed Iodine on an interplanetary CubeSat can provide ~2.5km/s of ∆V - Challenges with communications and attitude control over geocentric spacecraft - Enables Lunar orbiter, asteroid flyby and rendezvous missions for <$20M life cycle cost - Enables secondary missions via primary host deployment - Outer planet moons - Constellations Iodine enables high ∆V interplanetary propulsion ESPA Class Mission Concept – Lunar Orbiter Detailed ACO Study for Lunar Orbiter with “Discovery” science payload - Deployment from GTO - Iodine enabled 100x5km orbit station-keeping - Total life cycle cost ~$150M - Leveraged 2x BHT-600-I Thrusters Iodine / Electric Propulsion enables high value lunar orbiter science despite multiple previous lunar missions. Orbit Transfer Vehicles The direct replacement of xenon for iodine will significantly increase ∆V capability or enable additional payloads on the carrier vehicle. Iodine OTV can deliver large number of SmallSats / CubeSats from GTO to a range of Lunar orbits. Mid-Term Iodine Objectives Multiple Studies Completed on Enabling Applications: 1) 200 W Iodine is enabling for NanoSats (1-10kg) and MicroSats (10-100kg) - Iodine properties are ideal for secondary payloads - Benign propellant, quiescent until heated - Launches and stores unpressurized 3 3 - High density ~6g/cm and high Density – ISP ~ 8,000 g-s/cm - Xe ~3,000 g-s/cm3, Solid Motor ~500 g-s/cm3, Cold Gas ~150 g-s/cm3 - Enables orbit maneuverability (plane change and altitude change) - Enables spacecraft deorbit 2) 200W – 600W Iodine enables very high ∆V for ESPA class (180kg) spacecraft - Can provide ~10km/s ∆V - More than 2x the Xenon ∆V capability (Volume limited) - Enables GTO to Asteroids, Mars and Venus (Iodine and Xenon can both go to the moon) 3) 600W Iodine Enables “Discovery Class” Science Instruments for ESPA Grande class (300kg) spacecraft - Volume limitations require high density propellant - 3x – 5x reduction in total mission cost - New class of HEOMD and SMD missions 4) 600W – 1.5KW Class Iodine Enables Orbit Maneuvering Systems - Iodine based ESPA OMS can enable high ∆V using the volume within the ESPA ring - Can enable additional payloads over Xenon from GTO to GEO - Can enable independent payload delivery to various Mars orbits The technology can be enabling for a wide range of future commercial, academic, DoD and NASA HEOMD and SMD missions. iSAT Mission Concept Overview The iSAT Project is the maturation of iodine Hall technology to enable high ∆V primary propulsion for NanoSats (1-10kg), MicroSats (10-100kg) and MiniSats (100-500kg) with the culmination of a technology flight demonstration. - NASA Glenn is leading the technology development and is the flight propulsion system lead - Busek delivering the qualification and flight system hardware - NASA MSFC is leading the flight system development and operations The iSAT Project launches a small spacecraft into low-Earth orbit to: - Validate system performance in space - Demonstrate high ∆V primary propulsion - Reduce risk for future higher class iodine missions - Demonstrate new power system technology for SmallSats - Demonstrate new class of thermal control for SmallSats - Perform secondary science phase with contributed payload - Increase expectation of follow-on SMD and AF missions - Demonstrate SmallSat Deorbit - Validate iodine spacecraft interactions / efficacy High value mission for SmallSats and for future higher-class mission leveraging iodine propulsion advantages. iSAT Project Overview Mission Justification There is an emerging and rapidly growing market for SmallSats - SmallSats are significantly limited by primary propulsion - Desire to transfer to higher value science / operations orbit and responsive space - Desire to extend mission life / perform drag make-up - Requirement to deorbit within 25 years of end-of-mission Limitations on SmallSats limit primary propulsion options - Requirements imposed by nature of secondary payloads - Limitations for volume, mass and power - Limitations on hazardous and stored energy from propellants - Limitations for high pressure systems - Systems must sit quiescent for unknown periods before integration with primary Why perform flight validation? - Reduce risk of implementation of iodine for future higher class missions - Gain experience with condensable propellant spacecraft interactions - Reduce risk of custom support systems - Power generation, storage and distribution - Thermal control - Cost effective risk reduction before maturing higher power systems iSAT Project Overview Mission Justification 200W NanoSat infusion near-term with low entry cost and lower risk Short mission durations, low throughput requirement, simple propellant management Engineering / material changes and validation, valve wetting surfaces and seals Demonstrates enabling technology, demonstrates high spacecraft power density Additional high payoff for higher power / high payoff mission infusion Critical Technology Gaps and Risks Remain Propellant flow rate and metering is critical to achieve required performance Large propellant management, potentially conformal tanks Uniform / efficient heating and propellant management critical Wear testing >1000hrs for both thrusters and cathodes Additional material compatibility testing Spacecraft / plume interactions testing and analyses Sputter erosion data, erosion modeling and lifetime analyses Critical gaps remain for efficient propellant heating, transport and metering in a relevant environment in addition to long duration test data and analyses required for mid-term mission infusion. iSAT Project Overview Stakeholder Expectations The iSAT project is supported by a wide range of customers including: - MSFC Technology Investment Program (TIP) - MSFC Center Strategic Development Steering Group (CSDSG) - Office of the Chief Technologist (OCT) - Advanced Exploration Systems (AES) Program - Game Changing Development (GCD) Program - NASA Engineering and Safety Center (NESC) - Air Force: AFRL, ORS and SMC - Small Business Innovative Research (SBIR) Program Additional stakeholders include: - NASA Glenn to transition a new Electric Propulsion technology to flight - NASA MSFC to provide flight system development experience to young engineers - SmallSat
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